naa a22 4500 51076617X CHVBK 20180411083157.0 cr unu---uuuuu 180411e20131001xx s 000 0 eng 10.1007/s11630-013-0640-z doi (NATIONALLICENCE)springer-10.1007/s11630-013-0640-z Effects of inlet circumferential fluctuation on the sweep aerodynamic performance of axial fans/compressors [Elektronische Daten] [Xingmin Gui, Fang Zhu, Ke Wan, Donghai Jin] Swept blades have been widely used in the transonic fan/compressor of aircraft engines with the aids of 3D CFD simulation since the design concept of controlling the shock structure was firstly proposed and successfully tested by Dr. Wennerstrom in the 1980s. However, some disadvantage phenomenon has also been induced by excessively 3D blade geometries on the structure stress insufficiency, vibration and reliability. Much confusion in the procedure of design practice leading us to recognize a new view on the flow mechanism of sweep aerodynamical induction: the new radial equilibrium established by the influence of inlet circumferential fluctuation (CF) changes the inlet flows of blading and induces the performance modification of axial fans/compressors blade. The view is verified by simplified models through numerical simulation and circumferentially averaged analysis in the present paper. The results show that the CF source items which originate from design parameters, such as the spanwise distributions of the loading and blading geometries, contribute to the changing of averaged incidence spanwise distribution, and further more affect the performance of axial fans/compressors with swept blades. Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag Berlin Heidelberg, 2013 turbomachinery nationallicence fans/compressors nationallicence sweep aerodynamics nationallicence quasi-3D method nationallicence 3D flow nationallicence Gui Xingmin Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut Zhu Fang Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut Wan Ke Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut Jin Donghai Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut Journal of Thermal Science Springer Berlin Heidelberg 22/5(2013-10-01), 383-394 1003-2169 22:5<383 2013 22 11630 https://doi.org/10.1007/s11630-013-0640-z text/html Onlinezugriff via DOI 1 research-article jats NATIONALLICENCE 856 40 https://doi.org/10.1007/s11630-013-0640-z text/html Onlinezugriff via DOI NATIONALLICENCE 700 1- Gui Xingmin Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut NATIONALLICENCE 700 1- Zhu Fang Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut NATIONALLICENCE 700 1- Wan Ke Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut NATIONALLICENCE 700 1- Jin Donghai Aero-Engine Simulation Research Center, Beijing University of Aeronautics and Astronautics, 100191, Beijing, China aut NATIONALLICENCE 773 0- Journal of Thermal Science Springer Berlin Heidelberg 22/5(2013-10-01), 383-394 1003-2169 22:5<383 2013 22 11630 Metadata rights reserved Springer special CC-BY-NC licence nationallicence BK010053 XK010053 XK010000 NATIONALLICENCE NATIONALLICENCE NL-springer